CN107671640B - Grinding quick-change tool for precision part of fuel nozzle of aircraft engine and using method - Google Patents
Grinding quick-change tool for precision part of fuel nozzle of aircraft engine and using method Download PDFInfo
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- CN107671640B CN107671640B CN201710901629.7A CN201710901629A CN107671640B CN 107671640 B CN107671640 B CN 107671640B CN 201710901629 A CN201710901629 A CN 201710901629A CN 107671640 B CN107671640 B CN 107671640B
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- fuel nozzle
- aircraft engine
- positioning mandrel
- grinding
- precision
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B24—GRINDING; POLISHING
- B24B—MACHINES, DEVICES, OR PROCESSES FOR GRINDING OR POLISHING; DRESSING OR CONDITIONING OF ABRADING SURFACES; FEEDING OF GRINDING, POLISHING, OR LAPPING AGENTS
- B24B19/00—Single-purpose machines or devices for particular grinding operations not covered by any other main group
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B24—GRINDING; POLISHING
- B24B—MACHINES, DEVICES, OR PROCESSES FOR GRINDING OR POLISHING; DRESSING OR CONDITIONING OF ABRADING SURFACES; FEEDING OF GRINDING, POLISHING, OR LAPPING AGENTS
- B24B41/00—Component parts such as frames, beds, carriages, headstocks
- B24B41/06—Work supports, e.g. adjustable steadies
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- Grinding Of Cylindrical And Plane Surfaces (AREA)
Abstract
A grinding quick-change tool for precision parts of fuel nozzles of aircraft engines and a using method belong to the technical field of quick-change tools and comprise a transfer shaft, a positioning mandrel and a shifting fork screw assembly; the fuel nozzle precision part of the aircraft engine to be ground is arranged on the positioning mandrel, and then the positioning mandrel and the adapter shaft are connected and arranged on the grinding machine, so that the rapid clamping of the fuel nozzle precision part of the aircraft engine is changed, the problems of multiple times and low precision of appearance grinding and clamping of the fuel nozzle precision part of the aircraft engine are solved, repeated alignment in the clamping process is cancelled, the working difficulty of grinding operators is reduced, the production efficiency of the fuel nozzle precision part is improved, the processing precision and the product size consistency are improved, and the operation safety of the aircraft engine is ensured.
Description
Technical Field
The invention belongs to the technical field of quick-change tools, and particularly relates to a grinding quick-change tool for a precision part of a fuel nozzle of an aircraft engine and a using method of the grinding quick-change tool.
Background
Aircraft engine fuel nozzles are one of the important components of aircraft engines, the quality of which has a significant impact on the performance of the aircraft engine. The structure of the aircraft engine fuel nozzle is complex, the exterior of the aircraft engine fuel nozzle usually comprises a suspended conical surface section, a flange section, a groove section, a matching cylindrical section, a flow oil conical surface section and a flow oil cylindrical section, wherein the requirements of the taper, the diameter and the roughness of each section are different, and the appearance of the aircraft engine fuel nozzle is usually required to be ground in order to meet the use requirement.
The shape of the fuel nozzle of the aircraft engine is ground by an optical profile grinder, which is limited by the shape and an inner cavity structure, when the shape is ground, no part for direct clamping is available on the fuel nozzle of the aircraft engine, and at present, the fuel nozzle can only be clamped by a traditional double-center structure or a conversion reference by means of a shape clamping mode.
However, in actual processing, because the aircraft engine fuel nozzle has small structural size, complex appearance and high precision requirement, when the aircraft engine fuel nozzle is ground on an optical curve grinding machine, parts need to be repeatedly disassembled and assembled for a plurality of times to adjust the size or grind different parts, a traditional double-center structure or a conversion reference mode of clamping by virtue of the appearance is adopted, the disassembly and the assembly are inconvenient, the error is large after secondary clamping, the product size consistency is poor, the processing quality of a precision part of the nozzle is seriously influenced, meanwhile, the phenomenon that a grinding wheel is easy to interfere with the workpiece during grinding is easy to occur, an operator needs to be highly vigilant during grinding, the over-cutting is prevented, and the operation difficulty is high.
Disclosure of Invention
Aiming at the problems in the prior art, the invention provides a grinding quick-change tool for a precision part of a fuel nozzle of an aero-engine and a using method thereof, so that the machining precision of the precision part of the fuel nozzle of the aero-engine is improved, and the operation difficulty is reduced.
The invention is realized by the following technical scheme:
a grinding quick-change tool for precision parts of fuel nozzles of aircraft engines comprises a transfer shaft, a positioning mandrel and a shifting fork screw assembly;
one end of the adapter shaft is conical, the other end of the adapter shaft is provided with a U-shaped groove, and a positioning mandrel mounting hole is formed in one side, away from the conical end, of the U-shaped groove;
a connecting part is arranged on the positioning mandrel and is installed in a positioning mandrel installation hole, and a positioning sharp hole is formed in the other end of the positioning mandrel;
one end of the shifting fork screw assembly is connected with the positioning mandrel, and the other end of the shifting fork screw assembly is used for being connected with a shifting fork of the grinding machine.
Optionally, one end of the transfer shaft is provided with a second morse cone.
Optionally, the positioning mandrel mounting hole is a tapered hole, and the taper angle of the inner tapered surface is 60 °.
Optionally, the connecting portion is of a conical surface structure, and the conical angle of the outer conical surface is 60 °.
Optionally, the shifting fork screw assembly comprises a shifting fork screw and a fixing nut;
one end of the shifting fork screw is in threaded connection with the fixing nut, and the other end of the shifting fork screw is used for being connected with a shifting fork of the grinding machine;
the fixing nut is connected with the positioning mandrel.
Optionally, the diameter of the connector on the positioning core shaft is larger than the diameter of the joint of the inner cavity of the precision fuel nozzle part of the aircraft engine and the connector.
Optionally, the outer circumference of the connector on the positioning mandrel is plated with cadmium.
The invention provides a using method of any one of grinding quick-change tools for precision parts of fuel nozzles of aircraft engines, which comprises the following steps:
mounting a precision fuel nozzle piece of the aircraft engine on a connecting head at the end part of a positioning mandrel;
fixing the adapter shaft on a grinding machine, installing one end of a positioning mandrel provided with an aircraft engine fuel nozzle precision piece into a positioning mandrel installation hole, and installing the other end of the positioning mandrel on the grinding machine through the center of the grinding machine;
the shifting fork screw assembly connected with the shifting fork of the grinding machine drives the precision part of the fuel nozzle of the aircraft engine, which is arranged on the positioning core shaft, to rotate, and the precision part of the fuel nozzle of the aircraft engine is ground through the grinding wheel.
Compared with the prior art, the invention has the following beneficial technical effects:
according to the grinding quick-change tool for the fuel nozzle precision piece of the aircraft engine, the fuel nozzle precision piece of the aircraft engine to be ground is arranged on the positioning mandrel, and then the positioning mandrel and the adapter shaft are connected and arranged on the grinding machine, so that the quick clamping of the fuel nozzle precision piece of the aircraft engine is changed, the problems of multiple grinding and clamping times and low precision of the appearance of the fuel nozzle precision piece of the aircraft engine are solved, the repeated alignment in the clamping process is cancelled, the working difficulty of grinding operators is reduced, the production efficiency, the machining precision and the product size consistency of the fuel nozzle precision piece are improved, and the operation safety of the aircraft engine is ensured. And through the U-shaped groove that sets up on the switching axle, for the emery wheel provides working space, prevent to interfere.
Furthermore, the positioning mandrel mounting hole and the connecting part are of conical structures, so that the positioning mandrel can rotate in the positioning mandrel mounting hole, and the axial positioning of the positioning mandrel can be realized.
Furthermore, the diameter of the connector on the positioning mandrel is larger than the diameter of the joint of the inner cavity of the fuel nozzle precision piece of the aircraft engine and the connector, so that the connection strength of the positioning mandrel and the fuel nozzle precision piece of the aircraft engine is ensured.
The invention provides a using method of a grinding quick-change tool for a precision part of an aircraft engine fuel nozzle, wherein the precision part of the aircraft engine fuel nozzle is arranged on a connecting head at the end part of a positioning mandrel; the adapter shaft is fixed on a grinding machine, one end of a positioning mandrel provided with an aircraft engine fuel nozzle precision piece is arranged in a positioning mandrel mounting hole, the other end of the positioning mandrel is arranged on the grinding machine through the top of the grinding machine, so that the rapid clamping of the aircraft engine fuel nozzle precision piece is changed, the problems of multiple times of appearance grinding and clamping of the aircraft engine fuel nozzle precision piece and low precision are solved, the repeated alignment in the clamping process is cancelled, the working difficulty of grinding operators is reduced, the production efficiency, the processing precision and the product size consistency of the aircraft engine fuel nozzle precision piece are improved, and the operation safety of the aircraft engine is ensured.
Drawings
Fig. 1 is a schematic view of a grinding and quick-change tool for a precision part of a fuel nozzle of an aircraft engine, provided by an embodiment of the invention;
FIG. 2 is a flow chart of a method for using the grinding quick-change tool for the precision part of the fuel nozzle of the aircraft engine according to the embodiment of the invention;
FIG. 3 is a schematic illustration of an aircraft engine fuel nozzle precision provided by an embodiment of the present invention.
In the figure: 1. the fuel nozzle comprises a rotary connecting shaft, 2 parts of a positioning core shaft, 3 parts of a shifting fork screw, 4 parts of a fixing nut, 5 parts of an aircraft engine fuel nozzle precision part, 51 parts of a straight hole section, 52 parts of an inner conical surface section, 53 parts of a spray hole section, 54 parts of a suspension conical surface section, 55 parts of a flange section, 56 parts of a groove section, 57 parts of a matching cylinder section, 58 parts of a flowing oil conical surface section and 59 parts of a flowing oil cylinder section.
Detailed Description
The present invention will now be described in further detail with reference to specific examples, which are intended to be illustrative, but not limiting, of the invention.
As shown in figure 1, the grinding and quick-change tool for the precision part of the fuel nozzle of the aircraft engine comprises a transfer shaft 1, a positioning mandrel 2 and a shifting fork screw assembly; one end of the transfer shaft 1 is conical, the other end of the transfer shaft is provided with a U-shaped groove, and one side of the U-shaped groove, which is far away from the conical end, is provided with a mounting hole of the positioning mandrel 2; a connector is arranged at one end of the positioning mandrel 2 and is used for connecting an aircraft engine fuel nozzle precision piece 5, a connecting part of a transfer shaft 1 is arranged on the positioning mandrel 2, the connecting part of the transfer shaft 1 is arranged in a mounting hole of the positioning mandrel 2, and a positioning sharp hole is arranged at the other end of the positioning mandrel 2; one end of the shifting fork screw component is connected with the positioning mandrel 2, and the other end of the shifting fork screw component is used for being connected with a shifting fork of the grinding machine.
Wherein, one end of the adapting shaft 1 can be a second Morse cone. The mounting hole of the positioning mandrel 2 is a conical hole, and the conical angle of the inner conical surface is 60 degrees. Correspondingly, the connecting part of the adapter shaft 1 is of a conical surface structure, and the conical angle of the outer conical surface is 60 degrees.
The shifting fork screw component comprises a shifting fork screw 3 and a fixing nut 4; one end of the shifting fork screw 3 is in threaded connection with the fixing nut 4, and the other end of the shifting fork screw is used for being connected with a shifting fork of the grinding machine; the fixing nut 4 is connected with the positioning mandrel 2.
In order to ensure that the connection mode of the connector on the positioning mandrel 2 and the precision part 5 of the fuel nozzle of the aircraft engine is interference connection, the diameter of the connector on the positioning mandrel 2 is larger than the diameter of the connection part of the inner cavity of the precision part 5 of the fuel nozzle of the aircraft engine and the connector.
Cadmium plating may be applied to the outer circumference of the connector on the positioning mandrel 2 to prevent wear.
As shown in fig. 2, an application method of a quick-change tool for grinding a precision part of an aircraft engine fuel nozzle provided by an embodiment of the invention includes:
and 3, driving the precision part 5 of the fuel nozzle of the aircraft engine, which is arranged on the positioning core shaft 2, to rotate through a shifting fork screw assembly connected with a shifting fork of the grinding machine, and grinding the precision part 5 of the fuel nozzle of the aircraft engine through a grinding wheel.
By way of example, taking the grinding of the shape of the aircraft engine fuel nozzle precision part shown in fig. 3 as an example, the inner cavity of the aircraft engine fuel nozzle precision part 5 comprises three parts, namely a straight hole section 51, an inner conical surface section 52 and a spray hole section 53 from left to right, the inner diameter of the straight hole section 51 is 3-8mm, the tolerance level is IT7-IT8, the conical angle of the inner conical surface section 52 is 50-100 degrees, and the inner diameter of the straight hole section 51 is 0.3-1.3 mm; the appearance of the oil flow cone-shaped cylinder comprises six parts, namely a suspension cone-shaped section 54, a flange section 55, a groove section 56, a matching cylinder section 57, an oil flow cone-shaped section 58 and an oil flow cylinder section 59 from left to right, wherein the cone angle of the suspension cone-shaped section 54 is 80-180 degrees, the diameter of the flange section 55 is 10-20mm, the length is 0.8-1.5mm, the diameter of the groove section 56 is 6-10mm, the length is 5-8mm, the diameter of the matching cylinder section 57 is 8-14mm, the tolerance grade is IT7-IT8, the length is 0.8-1.2mm, the cone angle of the oil flow cone-shaped section 58 is 80-110 degrees, the diameter of the oil flow cylinder section 59 is 0.8-1.5mm, and the length is; the perpendicularity of the left end face of the groove section 56 relative to the cylindrical surface of the inner cavity straight hole section 51 is 0.01-0.03, and the coaxiality of an excircle M of the matched cylindrical section 57 relative to the inner cavity straight hole section 51 is phi 0.01-phi 0.05; the surface roughness Ra of the groove section 56, the matching cylindrical section 57, the oil flow conical surface section 58 and the oil flow cylindrical section 59 on the appearance is 0.2-0.8 mu m, and the integral appearance grinding is required to ensure the dimensional accuracy and the service performance requirements. The appearance of the utility model has the following functions: the left end surface of the groove section 56 is a sealing surface of a main oil path and an auxiliary oil path, so that oil leakage and leakage are prevented; the excircle of the matching cylindrical section 57 is matched with the inner hole of the nozzle, the flow of the main oil circuit and the auxiliary oil circuit flowing through the inner hole is limited, fuel oil flows through the swirl groove of the matching cylindrical section 57 as far as possible, the flow speed and the atomization effect of the flowing fuel oil are improved, the groove section 56, the oil flow conical section 58 and the oil flow cylindrical section 59 are fuel oil flowing surfaces, and the requirement of low surface roughness is favorable for weakening the speed attenuation amount when the fuel oil flows.
During grinding, the groove section 56, the matching cylindrical section 57, the oil flow cylindrical section 59 and the oil flow conical section 58 need to be ground. The specific method for grinding by using the invention is as follows: connecting a positioning mandrel 2 with a shifting fork screw assembly, positioning by using centre holes on the left side and the right side of the positioning mandrel 2 to form a double-centre structure, installing the positioning mandrel 2 connected with the shifting fork screw assembly on a machine tool, grinding an excircle, matching with a straight hole section 51 in an inner cavity of a precision part of an aircraft engine fuel nozzle to form tight fit, and matching and assembling into a part to be ground; the method comprises the steps of fixing a rotating shaft 1 on an optical curve grinding machine, clamping a matched and assembled to-be-ground part on the optical curve grinding machine, matching a center hole at the left end of a positioning core shaft 2 with a machine tool center, matching a middle 60-degree conical surface with the conical surface of the rotating shaft 1, adjusting the front and back positions of the machine tool center to determine the tight jacking, grinding a groove section 56, a matching cylindrical section 57, a flowing oil cylindrical section 59 and a flowing oil conical surface section 58 respectively, grinding different parts and adjusting the size without disassembling an aircraft engine fuel nozzle precision part 5, only loosening the machine tool center, and taking down or quickly replacing the to-be-ground part. When the positioning mandrel 2 is worn, the aim of reusing can be achieved by plating cadmium on the outer circle of the right end again.
The above description is only for the purpose of illustrating the preferred embodiments of the present invention and is not to be construed as limiting the invention, and any modifications, equivalents, improvements and the like that fall within the spirit and principle of the present invention are intended to be included therein.
Claims (6)
1. A grinding quick-change tool for a precision part of an aircraft engine fuel nozzle is characterized by comprising a transfer shaft (1), a positioning core shaft (2) and a shifting fork screw assembly;
one end of the transfer shaft (1) is conical, the other end of the transfer shaft is provided with a U-shaped groove, and a positioning mandrel mounting hole is formed in one side, away from the conical end, of the U-shaped groove;
a connector is arranged at one end of the positioning mandrel (2) and used for being connected with an aircraft engine fuel nozzle precision piece (5), a connecting part is arranged on the positioning mandrel (2) and installed in a positioning mandrel installation hole, and a positioning sharp hole is formed in the other end of the positioning mandrel (2); the diameter of the connector on the positioning mandrel (2) is larger than the diameter of the joint of the inner cavity of the precision fuel nozzle part of the aircraft engine and the connector; cadmium is plated on the outer circumference of the connector on the positioning mandrel (2);
one end of the shifting fork screw component is connected with the positioning mandrel (2), and the other end of the shifting fork screw component is used for being connected with a shifting fork of the grinding machine.
2. The grinding and quick-change tool for the precision part of the fuel nozzle of the aircraft engine as claimed in claim 1, wherein one end of the adapter shaft (1) is a second Morse cone.
3. The aircraft engine fuel nozzle precision part grinding quick-change tool as claimed in claim 1, wherein the positioning mandrel mounting hole is a tapered hole, and the taper angle of the inner conical surface is 60 °.
4. The grinding and quick-change tool for the precision part of the fuel nozzle of the aircraft engine as claimed in claim 1, wherein the connecting part is of a conical surface structure, and the conical angle of the outer conical surface is 60 degrees.
5. The grinding and quick-change tool for the precision part of the fuel nozzle of the aircraft engine as claimed in claim 1, wherein the shifting fork screw assembly comprises a shifting fork screw (3) and a fixing nut (4);
one end of the shifting fork screw (3) is in threaded connection with the fixing nut (4), and the other end of the shifting fork screw is used for being connected with a shifting fork of the grinding machine;
the fixing nut (4) is connected with the positioning mandrel (2).
6. The use method of the aircraft engine fuel nozzle precision part grinding quick-change tool based on any one of claims 1 to 5 is characterized by comprising the following steps:
mounting a precision fuel nozzle piece of the aircraft engine on a connecting head at the end part of a positioning mandrel;
fixing the adapter shaft on a grinding machine, installing one end of a positioning mandrel provided with an aircraft engine fuel nozzle precision piece into a positioning mandrel installation hole, and installing the other end of the positioning mandrel on the grinding machine through the center of the grinding machine;
the shifting fork screw assembly connected with the shifting fork of the grinding machine drives the precision part of the fuel nozzle of the aircraft engine, which is arranged on the positioning core shaft, to rotate, and the precision part of the fuel nozzle of the aircraft engine is ground through the grinding wheel.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710901629.7A CN107671640B (en) | 2017-09-28 | 2017-09-28 | Grinding quick-change tool for precision part of fuel nozzle of aircraft engine and using method |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710901629.7A CN107671640B (en) | 2017-09-28 | 2017-09-28 | Grinding quick-change tool for precision part of fuel nozzle of aircraft engine and using method |
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| Publication Number | Publication Date |
|---|---|
| CN107671640A CN107671640A (en) | 2018-02-09 |
| CN107671640B true CN107671640B (en) | 2020-01-07 |
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| CN201710901629.7A Active CN107671640B (en) | 2017-09-28 | 2017-09-28 | Grinding quick-change tool for precision part of fuel nozzle of aircraft engine and using method |
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Families Citing this family (2)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN110814878A (en) * | 2019-11-13 | 2020-02-21 | 中国航发动力股份有限公司 | Device for processing rubber sealing conical core |
| CN111750758B (en) * | 2020-06-30 | 2022-04-26 | 中国航发动力股份有限公司 | Method and device for detecting diameter and length size of conical surface and machining method |
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| JPS61188066A (en) * | 1985-02-12 | 1986-08-21 | Toyoda Mach Works Ltd | Grinding machine |
| CN102029537A (en) * | 2010-11-11 | 2011-04-27 | 西北工业大学 | Precise positioning fixture for numerical control machining of thin-wall blade |
| CN202317989U (en) * | 2011-11-25 | 2012-07-11 | 浙江浦江齿轮有限公司 | Device for clamping workpiece |
| CN103245268A (en) * | 2013-05-10 | 2013-08-14 | 西安航空动力股份有限公司 | Method for measuring nozzle vent length of aircraft engine |
| CN104493708A (en) * | 2014-11-20 | 2015-04-08 | 贵州汇强科技有限公司 | Positioning mandrel for effectively controlling coaxiality of bearing bushings and using method of positioning mandrel |
| CN204277779U (en) * | 2014-12-11 | 2015-04-22 | 中国直升机设计研究所 | A kind of Self-sealing valve lapping device |
| CN205342586U (en) * | 2016-02-19 | 2016-06-29 | 山东大学 | Fine special fixture that mills of high speed of small -size accurate work piece |
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2017
- 2017-09-28 CN CN201710901629.7A patent/CN107671640B/en active Active
Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPS61188066A (en) * | 1985-02-12 | 1986-08-21 | Toyoda Mach Works Ltd | Grinding machine |
| CN102029537A (en) * | 2010-11-11 | 2011-04-27 | 西北工业大学 | Precise positioning fixture for numerical control machining of thin-wall blade |
| CN202317989U (en) * | 2011-11-25 | 2012-07-11 | 浙江浦江齿轮有限公司 | Device for clamping workpiece |
| CN103245268A (en) * | 2013-05-10 | 2013-08-14 | 西安航空动力股份有限公司 | Method for measuring nozzle vent length of aircraft engine |
| CN104493708A (en) * | 2014-11-20 | 2015-04-08 | 贵州汇强科技有限公司 | Positioning mandrel for effectively controlling coaxiality of bearing bushings and using method of positioning mandrel |
| CN204277779U (en) * | 2014-12-11 | 2015-04-22 | 中国直升机设计研究所 | A kind of Self-sealing valve lapping device |
| CN205342586U (en) * | 2016-02-19 | 2016-06-29 | 山东大学 | Fine special fixture that mills of high speed of small -size accurate work piece |
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| CN107671640A (en) | 2018-02-09 |
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